Similarly shaped airfoils to GA 35-312
New! Bulk download of polars in Excel format: GA%2035-312.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (0) | Similarly shaped airfoils
Plain Flapped Shapes: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Basic Data: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl | Curve fits | Lift curve slopes
Data source comparison (Codes, CFD, Wind tunnel)
Compressibility Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Roughness Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Plain Flap Effects: cl,max vs flap deflection: all flap chords | 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cl vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cm vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cd vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
2. NACA63-412 a=0.5
3. NACA63-412 a=0.6
4. NACA64-412 a=0.5
5. EPPLER 207
6. NACA64-412 a=0.6
7. NM32 root
8. GA 35A312
9. NACA63-412 a=0.8
10. NACA63-412 a=0.2
11. NACA63-512
12. NACA64-412 a=0.8
13. GA 35-311
14. GA 35-313
15. HQ 2.5/12
16. GA 30-311
17. NACA64-412 a=0.2
18. NACA63-512 a=0.0
19. HN-984
20. GA 35A311
21. MID 327 12%